Exhibit 2 BRIO Technical Data

0220-EX-CN-2018 Text Documents

SpaceQuest, Ltd.

2018-03-07ELS_206027

BRIO Satellite Exhibit 2 File #: 0220-EX-CN-2018 Technical Information March 7, 2018 Submitted By SpaceQuest, Ltd. 3554 Chain Bridge Road Suite 400 Fairfax, VA 22030

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information Table of Contents 1 Ownership, Operations and Construction. ..................................................................... 3 2 Orbital Requirements. ................................................................................................... 3 3 Service Area. ................................................................................................................. 3 4 Satellite Payload. .......................................................................................................... 3 5 Principle Specifications.................................................................................................. 4 6 System Block Diagram. .................................................................................................. 4 7 Telemetry, Tracking & Command and Payload Operations ............................................. 5 8 Radio Equipment........................................................................................................... 6 8.1 UHF TT&C Transceiver ........................................................................................................6 8.1.1 Downlink: UHF Transmit ........................................................................................................................6 8.1.2 Uplink: UHF Receive ...............................................................................................................................6 8.2 VHF Receiver: ....................................................................................................................6 8.3 S-Band Transceiver: ...........................................................................................................6 8.3.1 Downlink: S-Band Transmit ....................................................................................................................6 8.3.2 Uplink: S-Band Receive ..........................................................................................................................7 8.4 UHF Experimental Payload Transceiver ...............................................................................7 8.4.1 Downlink: UHF Transmit ........................................................................................................................7 8.4.2 Uplink: UHF Receive ...............................................................................................................................7 9 Antenna Systems .......................................................................................................... 8 10 Satellite Link Budgets .................................................................................................... 9 11 Interference Analysis .................................................................................................. 14 11.1 400.50-400.65 MHz (TT&C and Experimental Downlink) .................................................... 14 11.2 399.90 -400.05 MHz (TT&C and Experimental Uplink)........................................................ 14 11.3 2288-2289 MHz (Payload Downlink) ................................................................................. 14 11.4 2045-2046 MHz (Payload Uplink) ...................................................................................... 15 12 Power Flux Density Analysis ........................................................................................ 15 12.1 400.50-400.65 MHz (TT&C Downlink) ............................................................................... 15 12.2 2288-2289 MHz (S-Band Downlink)................................................................................... 16 12.3 400.50-400.65 MHz (Experimental Payload Downlink) ...................................................... 16 13 Space Station Antenna Radiation Patterns................................................................... 17 13.1 S-Band: BRIO Space Station Transmit/Receive Antenna .................................................... 17 13.2 UHF: BRIO Space Station TT&C Transmit/Receive Antenna ................................................ 17 13.3 VHF: BRIO Space Station Receive Antenna ........................................................................ 18 13.4 UHF: BRIO Space Station Experimental UHF Receive/Transmit Antenna ............................ 18 13.5 Summary of BRIO Antenna Characteristics........................................................................ 19 14 Earth Station Antenna Radiation Patterns ................................................................... 19 14.1 UHF TT&C Antennas in Fairfax, VA, North Pole, AK and Naalehu, HI and Limestone, ME .... 19 14.2 VHF Backup Antennas in Fairfax, VA, North Pole, AK and Naalehu, HI and Limestone, ME .. 20 14.3 S-Band Earth Station Antenna in North Pole Alaska and Limestone, Maine. ....................... 20 14.4 UHF Experimental Antenna in Fairfax, VA ......................................................................... 21 15 Stop Buzzer POC.......................................................................................................... 21 Exhibit 2 SpaceQuest PAGE 1

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information List of Figures Figure 1 Orbital Parameters............................................................................................................ 3 Figure 2 System Block Diagram....................................................................................................... 5 Figure 3 Isometric view of deployed configuration. ....................................................................... 5 Figure 4 Summary of BRIO Transmitter and Receiver parameters. ............................................... 8 Figure 5 Antenna Frequency Registration ..................................................................................... 8 Figure 6 Frequency Emissions Registration .................................................................................... 8 Figure 7 Satellite UHF TT&C Uplink Budget .................................................................................... 9 Figure 8 Satellite UHF TT&C Downlink Budget ............................................................................... 9 Figure 9 Satellite S-Band Uplink Budget ....................................................................................... 10 Figure 10 Satellite S-Band Downlink Budget ................................................................................ 10 Figure 11 Satellite Experimental UHF Uplink Budget ................................................................... 11 Figure 12 Satellite Experimental UHF Downlink Budget .............................................................. 11 Figure 13 Satellite VHF Uplink Budget .......................................................................................... 12 Figure 14 Satellite VHF Link Margins Vs. Elevation Angle ............................................................ 12 Figure 15 Satellite UHF TT&C Link Margins Vs. Elevation Angle .................................................. 13 Figure 16 Satellite S-Band Link Margins Vs. Elevation Angle ........................................................ 13 Figure 17 Satellite UHF Experimental Radio Link Margins Vs. Elevation Angle ............................ 14 Figure 18 PFD at the Surface of the Earth for the UHF Transmitter............................................. 15 Figure 19 PFD at the Surface of the Earth for the S-Band Transmitter ........................................ 16 Figure 20 PFD at the Surface of the Earth for the UHF Payload Transmitter ............................... 16 Figure 21 S-Band Satellite Transmit/Receive Antenna Radiation Pattern ................................... 17 Figure 22 TT&C UHF Satellite Transmit/Receive Antenna Radiation Pattern. ............................. 17 Figure 23 VHF Satellite Receive Antenna Radiation Pattern ........................................................ 18 Figure 24 Experimental UHF Satellite Transmit/Receive Antenna Radiation Pattern ................. 19 Figure 25 BRIO Antenna Characteristics ....................................................................................... 19 Figure 26 UHF Earth Station Antenna Radiation Pattern. ............................................................ 20 Figure 27 VHF Earth Station Antenna Radiation Pattern.............................................................. 20 Figure 28 S-Band Earth Station Antenna Radiation Pattern ......................................................... 21 Figure 29 UHF Experimental Earth Station Antenna Radiation Pattern ....................................... 21 Exhibit 2 SpaceQuest PAGE 2

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information 1 Ownership, Operations and Construction. SpaceQuest, Ltd. is a small business concern, and the owner, manufacturer and operator of the BRIO satellite. SpaceQuest has selected Spaceflight Industries of Seattle, Washington as the launch provider. BRIO will be launched on a SpaceX Falcon 9 launch vehicle from Vandenberg, AFB in California (geographic coordinates 34.5762°N; 4.2803°W) in July 2018. Pursuant to Part 5 §5.64 of the Commission’s Rules, construction of the proposed experimental satellite and associated facilities has begun prior to the Commission’s grant of an authorization. This is necessary given the nature of satellite construction and technical requirements over long lead times. Such construction is entirely at SpaceQuest’s risk without any assurances that its proposed experiment will be subsequently approved.  Space Station Name: BRIO  BRIO Estimated Construction Completion Date: May 2018  Spaceflight Final Certification of Licenses (Go/NoGo): May 31, 2018  Purpose: Experimental, non-Common Carrier basis  Orbital Type: NGSO 2 Orbital Requirements. The satellite is designed to operate in a circular sun-synchronous orbit as described in Figure 1. The satellites are based on COTS technology that allows for small, lightweight and low-cost spacecraft. BRIO Value Total Number of Orbital Planes: 1 Celestial Reference Body: Earth Inclination Angle (degrees): 97.52 Orbital Period (seconds) 5760 Apogee 575 km Perigee 575 km Figure 1 Orbital Parameters 3 Service Area. United States 4 Satellite Payload. The primary satellite mission of BRIO is to investigate, identify and resolve potential technical and implementation issues with its advanced satellite SDR radio design. Another important objective is to demonstrate the ability to upload and run new firmware that can introduce new features to the SDR Radio after it is on orbit. The results of this three-phase experiment will (1) demonstrate and validate the ability to uplink large numbers of messages to a satellite using a single channel, (2) demonstrate the ability to downlink messages to different ground devices on a single channel, and (3) implement an advanced Exhibit 2 SpaceQuest PAGE 3

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information signal processing algorithm on board a satellite to provide highly spectrally efficient bidirectional communications. The secondary satellite mission of BRIO is to test a backup receiver developed by SpaceQuest to send executive commands, to reboot the satellite flight computer, or to cycle the spacecraft power bus in the event of a system failure. As a components manufacturer, it is expected that the outcome of this testing will result in a significant advancement in satellite radio equipment technology. The BRIO UHF frequency assignment will be used for satellite telemetry, command and control. The S-Band assignment will be used to download selected mission data from the Myriota payload and upload new computer firmware to improve performance and correct any software deficiencies. 5 Principle Specifications. BRIO is a 3U CubeSat whose outside envelope measures 100 x 100 x 340.5mm. The satellite’s total mass is 5 kg. It has four deployable solar arrays, which deploy from the short edges of the spacecraft. The LiIon battery consists of eight cells wired as 4-series and 2 parallel. The expected mission lifetime is 5 years in a 575-km orbit due to battery life and deorbit analysis. SpaceQuest will own and operate the experimental CubeSat throughout its mission lifetime. The BRIO satellite will not be sold or transferred to another party. 6 System Block Diagram. Figure 2 below shows the major components of the spacecraft and their interfaces. The flight computer is responsible for TT&C and payload scheduling. The attitude determination and control system orients the solar panels to the sun, except when the satellite is re-oriented to communicate with a ground station. The Software Defined Radio shown below is for an S-Band transceiver. The deployed array and antenna configuration is shown in Figure 3. Command Receiver Exhibit 2 SpaceQuest PAGE 4

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information Figure 2 System Block Diagram Figure 3 Isometric view of deployed configuration. This configuration allows for two VHF and two UHF monopole antennas deployed from the body of the spacecraft. One UHF antenna is used for TT&C communication. The second UHF antenna is grounded. A third UHF antenna that is deployed from the side of the satellite when the solar panels are deployed is for a UHF SDR transceiver, which is a part of the experimental communications payload being evaluated for the hosted Myriota payload. The receive-only VHF monopole antennas are used to test a new backup receiver design to send executive commands to reboot the satellite flight computer in the event of a system failure. 7 Telemetry, Tracking & Command and Payload Operations The space-to-Earth downlink frequency band of 400.50-400.65 MHz and the Earth-to-space uplink frequency band of 399.90-400.05 MHz for TT&C communications will communicate with SpaceQuest’s Earth stations in Fairfax, Virginia, Naalehu, Hawaii, North Pole, Alaska, and Limestone, Maine. The SpaceQuest TT&C Earth stations will also have the capability to uplink executive commands to a backdoor command receiver at 145.92 MHz. The second UHF Transceiver used to evaluate Myriota’s advanced communications processor will also operate in the space-to-Earth downlink frequency band of 400.50- 400.65 MHz and the Earth-to-space uplink frequency band of 399.90-400.05 MHz. The space-to-Earth frequency band of 2288-2289 MHz will be used to downlink experimental test data to SpaceQuest’s Earth stations in North Pole, Alaska and Limestone, Exhibit 2 SpaceQuest PAGE 5

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information Maine. The Earth-to-space uplink frequency band of 2045-2046 MHz from LimeStone, Maine will be used occasionally to upload new firmware to the Myriota payload. 8 Radio Equipment. 8.1 UHF TT&C Transceiver  NanoComm AX100 UHF Transceiver manufactured by GomSpace.  Primary transceiver capability for telecommand, telemetry, and schedule uploads.  The transceiver can operate between 390 and 406 MHz at 9600 bps. modulation. 8.1.1 Downlink: UHF Transmit  Operating Frequency 400.60 MHz  Output Power: 3 Watts  EIRP: 3.3 dBW  Channels: 400.50-400.65 MHz  Frequency Deviation: 16 kHz 8.1.2 Uplink: UHF Receive  Operating Frequency 399.95 MHz  Sensitivity: -110 dBm  Channels: 399.90-400.05 MHz  Frequency Stability: ±10 ppm. 8.2 VHF Receiver:  CERX-145 Narrowband FM Receiver manufactured by SpaceQuest  Experimental backup VHF Receiver for emergency reboot or power cycle  145.92 MHz fixed receive frequency  GMSK modulation at 9600bps.  Sensitivity: -119 dBm 8.3 S-Band Transceiver:  GomSpace TR600 S-Band SDR Transceiver  Primary transceiver for mission data and commands to primary payload.  Space-to-Earth downlink operates from 2220 to 2290 MHz  Earth-to-space uplink operated from 2025 to 2110 MHz  700 Kbps data rate with QPSK modulation. 8.3.1 Downlink: S-Band Transmit  Requested Frequency 2288-2289 MHz  Output Power: 1 Watts  Peak antenna Gain: 7 dBi  EIRP: 3.3 dBW  Data Rate: 700 kbps Exhibit 2 SpaceQuest PAGE 6

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information  Channels: Tunable SDR Transmitter from 2220-2291MHz  Necessary Bandwidth: 1,000 kHz. 8.3.2 Uplink: S-Band Receive  Operating Frequency 2045-2046 MHz  Sensitivity: -100 dBm  Data Rate: 700 kbps  Channels: Tunable SDR Receiver from 2025-2110 MHz  Frequency Stability: ±10 ppm 8.4 UHF Experimental Payload Transceiver  ERP-100 UHF Transceiver manufactured by SpaceQuest.  UHF transceiver to be used with Myriota’s experimental payload processor.  The transceiver can operate between 390 MHz and 406 MHz at 9600 bps.  Modulation is FM/GMSK 8.4.1 Downlink: UHF Transmit  Operating Frequency 400.60 MHz  Output Power: 4 Watts  EIRP: 4.5 dBW  Channels: 400.50-400.65 MHz  Frequency Deviation: 16 kHz 8.4.2 Uplink: UHF Receive  Operating Frequency 399.95 MHz  Sensitivity: -112 dBm  Channels: Tunable SDR  Frequency Stability: ±10 ppm. Exhibit 2 SpaceQuest PAGE 7

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information A summary of the BRIO Transmitter and Receiver parameters are provided in Figure 4. Transmitter Transmitter Transmitter Receiver 1 Receiver 2 Receiver 3 Receiver 4 Description 1 2 3 Radio Name UTX SBTX EXTX URX SBRX EXRX VRX Carrier Frequency, MHz 400.6 2288.5 400.6 399.95 2045.5 399.95 145.92 3 dB Bandwidth, MHz 0.015 0.75 0.015 0.015 0.75 0.015 0.015 Necessary Bandwidth, MHz 0.035 1.0 0.035 0.035 1.0 0.035 0.035 20 dB Bandwidth, MHz 0.020 0.80 0.020 NA NA NA NA 60 dB Bandwidth, MHz 0.035 0.90 0.035 NA NA NA NA Receiver Sensitivity, dBm NA NA NA -110 -100 -110 -119 Antenna Gain, dBi 0.0 7.0 0.0 0.0 7.0 0.0 0.0 Modulation Type GMSK QPSK GMSK GMSK QPSK GMSK GMSK Total Data Rate (KHz) 9.6 700 9.6 9.6 700 9.6 9.6 Receiver Span (MHz) NA NA NA 0.15 1.0 0.15 0.05 EIRP, dBW 3.3 3.4 4.5 NA NA NA NA Antenna Polarization Linear Circular Linear Linear Circular Linear Linear Figure 4 Summary of BRIO Transmitter and Receiver parameters. 9 Antenna Systems The antenna frequency parameters for the BRIO Satellite are provided in Figure 5. Lower Upper Freq. Power Output ERP Mean/ Frequency Station Beam Power Frequency Frequency Units Units Power/ERP Units Peak Tolerance Class SBTX 2288.0 2289.0 MHz 1.0 W 3.4 dBW Peak +/-10 ppm Mobile UTX 400.50 400.65 MHz 3.0 W 3.3 dBW Peak +/-10 ppm Mobile EXTX 400.50 400.65 MHz 4.0 W 4.5 dBW Peak +/-10 ppm Mobile Figure 5 Antenna Frequency Registration The antenna emission parameters for the BRIO Satellite are provided in Figure 6. Lower Upper Modulating Necessary Beam Units Emission Frequency Frequency Signal Bandwidth SBTX 2288.0 2289.0 MHz 1M00G1D QPSK 1,000 KHz UTX 400.50 400.65 MHz 35K0F1D GMSK 35KHz EXTX 400.50 400.65 MHz 35K0F1D GMSK 35KHz Figure 6 Frequency Emissions Registration Exhibit 2 SpaceQuest PAGE 8

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information 10 Satellite Link Budgets The UHF TT&C uplink budget is shown in Figure 7. Figure 8 shows the TT&C downlink budget. Figure 7 Satellite UHF TT&C Uplink Budget Figure 8 Satellite UHF TT&C Downlink Budget Exhibit 2 SpaceQuest PAGE 9

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information The S-Band uplink budget is shown in Figure 9. Figure 10 shows the S-Band downlink budget. Figure 9 Satellite S-Band Uplink Budget Figure 10 Satellite S-Band Downlink Budget Exhibit 2 SpaceQuest PAGE 10

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information The UHF Experimental Payload uplink budget is shown in Figure 11. Figure 11 Satellite Experimental UHF Uplink Budget The UHF Experimental Payload downlink budget is shown in Figure 12. Figure 12 Satellite Experimental UHF Downlink Budget Exhibit 2 SpaceQuest PAGE 11

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information The VHF uplink budget is shown in Figure 13. The VHF Uplink Margin is plotted in Figure 14. Figure 13 Satellite VHF Uplink Budget VHF Uplink Margin 35 30 25 20 Link Margin (dB) 15 Backup Command Link 145MHz at 9.6 kbps 10 Watts Uplink Power 10 0.0 dBi Sat Antenna Gain 8.0 Grounds Antenna Gain 575 km Altitude 5 0 0 15 30 45 60 75 90 Elevation Angle (Degrees) Figure 14 Satellite VHF Link Margins Vs. Elevation Angle Exhibit 2 SpaceQuest PAGE 12

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information The satellite link margins for the UHF TT&C radio are plotted in Figure 15. UHF Link Margins 35 Down link Margin 30 Uplink Margin Link Margin (dB) 25 20 15 Command & Telemetry Links 400 MHz at 9.6 kbps 10 10 Watts Uplink Power 3 Watt Sat Transmit Power 0.0 dBi Sat Antenna Gain 5 13.5 Grounds Antenna Gain 0 0 15 30 45 60 75 90 Elevation Angle (Degrees) Figure 15 Satellite UHF TT&C Link Margins Vs. Elevation Angle The satellite link margins for the S-Band radio are plotted in Figure 16. S-Band Link Margins 30 UPLINK MA RGIN (dB) DOWNLINK MARGIN ( dB) 25 Link Margin (dB) 20 15 Mission Data Links 10 2045 and 2288 MHz at 700 Kbps 10 Watts Uplink Power 1 Watt Sat Transmit Power 7.0 dBi Sat Antenna Gain 5 40 dBi Ground Antenna Gain 575 km Altitude 0 0 15 30 45 60 75 90 Elevation Angle (Degrees) Figure 16 Satellite S-Band Link Margins Vs. Elevation Angle Exhibit 2 SpaceQuest PAGE 13

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information The satellite link margins for the UHF Experimental Transceiver is plotted in Figure 17. Experimental Payload Link Margins 16 Down link Margin 14 Uplink Margin 12 Link Margin (dB) 10 8 Experimental Payload Links 400 MHz at 9.6 kbps 6 3 Watts Uplink Power 4 Watt Sat Transmit Power 4 0.0 dBi Sat Antenna Gain 0.0 Grounds Antenna Gain 2 575 km Altitude 0 0 15 30 45 60 75 90 Elevation Angle (Degrees) Figure 17 Satellite UHF Experimental Radio Link Margins Vs. Elevation Angle 11 Interference Analysis 11.1 400.50-400.65 MHz (TT&C and Experimental Downlink) Interference with U.S. federal and commercial assignments in the 400.50-400.65 MHz band is unlikely as transmissions will only occur while over the SpaceQuest TT&C ground stations. The 400.50 to 400.65 MHz space-to-Earth band is allocated for UHF Little LEO data services. 11.2 399.90 -400.05 MHz (TT&C and Experimental Uplink) Interference with U.S. federal and commercial assignments in the 399.00-400.05 MHz band is unlikely as uplink transmissions will only occur while over the SpaceQuest TT&C ground stations. The 399.0-400.05 MHz Earth-to-space band is allocated for UHF Little LEO data services. 11.3 2288-2289 MHz (Payload Downlink) The GomSpace S-Band SDR transmitter is designed to operate in the 2220-2290 MHz band, but can operate slightly higher with some performance loss. Operation above 2292 MHz is not possible. The 2288-2289 MHz downlink band was chosen for the BRIO satellite, but any other 1.0 MHz channel in the 2220-2291 MHz band would be acceptable. S-Band downlink operations will occur several times each day at either North Pole, AK or Limestone, ME. Exhibit 2 SpaceQuest PAGE 14

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information Transmissions will be restricted as necessary to eliminate interference with other users of the band. 11.4 2045-2046 MHz (Payload Uplink) SpaceQuest’s S-Band satellite receiver is designed to operate in the 2025-2110 MHz band. A 1.0 MHz channel between 2045-2046 MHz was chosen because it appears to have the fewest number of license assignments. Infrequent S-Band uplink transmissions from Limestone, ME will be used to load new firmware to the BRIO satellite and to send confirmations of successful data packet downloads. Any 1.0 MHz channel within the 2025- 2010 MHz band would be acceptable for the BRIO experiment. 12 Power Flux Density Analysis 12.1 400.50-400.65 MHz (TT&C Downlink) The Power Flux Density for the UHF TT&C downlink is shown in Figure 18. UHF Power Flux Density Vs. Elevation Angle -120 Power Flux Density (dBW/m2/4kHz) -125 -130 -135 ITU Power Flux Density Limits Power Flux Density (dBW/m2/4kHz) -140 -145 0 10 20 30 40 50 60 70 80 90 Elevation Angle (deg) Figure 18 PFD at the Surface of the Earth for the UHF Transmitter Exhibit 2 SpaceQuest PAGE 15

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information 12.2 2288-2289 MHz (S-Band Downlink) The PFD for the S-Band downlink satisfies the ITU PFD limits as shown in Figure 19. S-Band Power Flux Density Vs. Elevation Angle -140.0 -142.0 -144.0 PFD (dBW/m^2/4 kHz) -146.0 -148.0 -150.0 -152.0 -154.0 ITU Power Flux Density Limits -156.0 Power Flux Density (dBW/m2/4kHz) -158.0 -160.0 0 10 20 30 40 50 60 70 80 90 Elevation Angel (Deg) Figure 19 PFD at the Surface of the Earth for the S-Band Transmitter 12.3 400.50-400.65 MHz (Experimental Payload Downlink) The Power Flux Density for the UHF Experimental Payload downlink is shown in Figure 20. Experimental Payload PDF Vs. Elevation Angle -120 Power Flux Density (dBW/m2/4kHz) -125 -130 -135 ITU Power Flux Density Limits Power Flux Density (dBW/m2/4kHz) -140 -145 0 10 20 30 40 50 60 70 80 90 Elevation Angle (deg) Figure 20 PFD at the Surface of the Earth for the UHF Payload Transmitter Exhibit 2 SpaceQuest PAGE 16

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information 13 Space Station Antenna Radiation Patterns 13.1 S-Band: BRIO Space Station Transmit/Receive Antenna The GomSpace NanoCom ANT2150 side-mounted S-Band Patch Antenna is used to downlink the BRIO mission data. This circularly-polarized antenna incorporates an LNA designed to receive in the 2025-2110 MHz frequency band, and a Power Amplifier designed to transmit in the 2200-2290 MHz frequency band. The radiation pattern is shown in Figure 21. 0 345 10 15 330 5 30 315 0 45 -5 300 -10 60 -15 285 -20 75 -25 270 -30 90 255 105 240 120 225 135 210 150 195 165 180 Figure 21 S-Band Satellite Transmit/Receive Antenna Radiation Pattern 13.2 UHF: BRIO Space Station TT&C Transmit/Receive Antenna An ISIS Deployable Omnidirectional UHF Monopole Antenna System is used to uplink and downlink TT&C data. It has a 0 dBi average gain and a radiation pattern shown in Figure 22. Figure 22 TT&C UHF Satellite Transmit/Receive Antenna Radiation Pattern. Exhibit 2 SpaceQuest PAGE 17

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information 13.3 VHF: BRIO Space Station Receive Antenna The same ISIS Deployable Omnidirectional Antenna has a VHF monopole element, which is used to receive emergency commands to reboot the flight computer or to power cycle the spacecraft in the event of a single event latch up. This small, sensitive, very low-power receiver design that operates at a different, fixed frequency than the primary UHF TT&C receiver, can save a mission. SpaceQuest will perform sensitivity tests of the receiver in order to characterize its performance in the space environment. The omni-directional radiation pattern is shown in Figure 23. Figure 23 VHF Satellite Receive Antenna Radiation Pattern 13.4 UHF: BRIO Space Station Experimental UHF Receive/Transmit Antenna An UHF Experimental Transceiver developed by SpaceQuest to investigate the performance of Myriota’s novel protocol and processing algorithms is shown in Error! Reference source not found.. Exhibit 2 SpaceQuest PAGE 18

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information Figure 24 Experimental UHF Satellite Transmit/Receive Antenna Radiation Pattern 13.5 Summary of BRIO Antenna Characteristics Figure 25 lists the antenna parameters for the four BRIO antennas. Antenna Parameter S-Band UHF VHF UHF Payload Frequency Range: 2025-2291 MHz 399.9-400.6 MHz 145.92 MHz 399.9-400.6 MHz Bandwidth Required: 900 KHz 100 KHz 25 KHz 100 KHz Emission Designator: 1M00G1D 35K0F1D 20K0F1D 35K0F1D Number of Channels: 1 1 1 1 Space Station Class: EH ET ED EH Beam Name: SBTX and SBRX UTX and URX VRX EXTX and EXRX Emission/Receive E/R E/R R E/R Max ISO. Gain 7.0 dBi 0.0 dBi 0.0 dBi 0.0 dBi Antenna Type: Patch Monopole Monopole Monopole Polarization: Circular Linear Linear Linear Peak Power: 1.0 Watts 3.0 Watts Receive Only 4.0 Watts See Error! Antenna Pattern: See Figure 21 See Figure 22 See Figure 23 Reference source not found. Link Margin: See Figure 16 See Figure 15 Receive Only See Figure 17 Within ITU limits. Within ITU limits. Within ITU limits. Power Flux Density: Receive Only See Figure 19 See Figure 18 See Figure 20 Figure 25 BRIO Antenna Characteristics 14 Earth Station Antenna Radiation Patterns The antenna pattern for SpaceQuest’s UHF Earth Stations are provided in Figure 26. Exhibit 2 SpaceQuest PAGE 19

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information 14.1 UHF TT&C Antennas in Fairfax, VA, North Pole, AK and Naalehu, HI and Limestone, ME Figure 26 UHF Earth Station Antenna Radiation Pattern. 14.2 VHF Backup Antennas in Fairfax, VA, North Pole, AK and Naalehu, HI and Limestone, ME The antenna patterns for SpaceQuest’s VHF Earth Stations are provided in Figure 27. Figure 27 VHF Earth Station Antenna Radiation Pattern. 14.3 S-Band Earth Station Antenna in North Pole Alaska and Limestone, Maine. SpaceQuest’s S-Band antennas in Alaska and Maine are for downloading the spectrum data captured by the Myriota payload. Only the Maine S-Band uplink will be used to upload new Exhibit 2 SpaceQuest PAGE 20

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information firmware to the satellite. An S-Band radiation pattern for these antennas is shown in Error! Reference source not found. Vertical Pattern Horizontal Pattern Figure 28 S-Band Earth Station Antenna Radiation Pattern 14.4 UHF Experimental Antenna in Fairfax, VA The radiation pattern for the omni-directional transceiver antenna that communicates with the UHF experimental payload on BRIO is depicted in Figure 29. 400.00 MHz Figure 29 UHF Experimental Earth Station Antenna Radiation Pattern Exhibit 2 SpaceQuest PAGE 21

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018 Technical Information 15 Stop Buzzer POC The 24-hour SpaceQuest contact for interference issues is provided below: Name: Glenn Richardson Email: glenn@spacequest.com Tel: 703-424-7806 Exhibit 2 SpaceQuest PAGE 22


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Document Modified: 2018-03-07 14:07:51
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